Measurement of magnetic field gradients

ABSTRACT

Technology for performing magnetic field gradient measurements is described. The magnetic field gradient measurements for specific positions on the Earth can be performed from a moving platform. The magnetic field gradient measurements can be identified as being affected by a level of error that exceeds a defined threshold. A correction value can be generated to compensate for the error in the magnetic field gradient measurements. The correction value can be applied to the magnetic field gradient measurements in order to obtain magnetic field gradient measurements with a reduced level of error.

BACKGROUND

The Earth's magnetic field, also known as a geomagnetic field, is amagnetic field that extends from the Earth's interior to a region abovethe Earth that is exposed to solar wind (i.e., a stream of chargedparticles that are exposed from the Sun). Magnetic fields are vectorquantities that are characterized by both strength and direction. Themagnitude of the Earth's magnetic field at the Earth's surface can rangefrom 20 to 80 microtesla (mT). This range is equal to 0.20 to 0.80 gaussor 20,000 to 80,000 nanotesla (nT). The magnitude of the Earth'smagnetic field can vary depending on location.

Magnetic field variations due to magnetic anomalies can be in thepicotesla (pT) range. In general, magnetic anomalies are localvariations in the Earth's magnetic field resulting from variations inthe chemistry or magnetism of the rocks. For example, magnetic surveysover the oceans have revealed a characteristic pattern of anomaliesaround mid-ocean ridges. These patterns involve a series of positive andnegative anomalies in the intensity of the magnetic field, which formstripes running parallel to each ridge. The source of these magneticanomalies can be from magnetization carried by titanomagnetite mineralsin basalt and gabbros, which are magnetized when ocean crust is formedat the ridge.

The Earth's magnetic field and magnetic field anomalies can be measuredusing a measurement instrument referred to as a magnetometer. Examplesof magnetometer include vector magnetometers and scalar magnetometers.Vector magnetometers can measure vector components of the Earth'smagnetic field. Scalar magnetometers can measure the magnitude of avector magnetic field. Magnetometers can also be classified based ontheir intended use. For example, stationary magnetometers can beinstalled to a fixed position and measurements are taken when themagnetometer is stationary. On the other hand, portable magnetometersare usable while in motion and can be transported in a moving vehicle.

BRIEF DESCRIPTION OF THE DRAWINGS

Features and advantages of the disclosure will be apparent from thedetailed description which follows, taken in conjunction with theaccompanying drawings, which together illustrate, by way of example,features of the disclosure; and, wherein:

FIG. 1 illustrates a system for determining a magnetic field gradient ofthe Earth using a magnetometer installed on a moving platform inaccordance with an example;

FIG. 2 illustrates a system and related operations for determining amagnetic field gradient of the Earth using a magnetometer installed on amoving platform in accordance with an example;

FIG. 3 illustrates a magnetometer on a moving platform that periodicallymeasures a magnetic field gradient of the Earth in accordance with anexample;

FIG. 4 illustrates matching a sequence of magnetic field gradientmeasurements to a reference magnetic field gradient map in accordancewith an example;

FIG. 5 illustrates a technique for measuring a magnetic field gradientin accordance with an example;

FIG. 6 illustrates an output of a magnetometer in accordance with anexample;

FIG. 7 illustrates a technique for computing a magnetic field gradientin accordance with an example;

FIG. 8 illustrates a system and related operations for determining ageographical location of a moving vehicle based on a plurality ofmagnetic field gradient measurements of the Earth in accordance with anexample;

FIG. 9 depicts a flow chart of a method for determining a magnetic fieldgradient in accordance with an example;

FIG. 10 depicts a flow chart of a method for determining a magneticfield gradient in accordance with an example;

FIG. 11 depicts a system for determining a magnetic field gradient inaccordance with an example.

FIG. 12 depicts a flow chart of a method for determining a geographicallocation of a moving platform in accordance with an example;

FIG. 13 depicts a flow chart of a method for determining a geographicallocation in accordance with an example; and

FIG. 14 depicts a system for determining a geographical location of amoving platform in accordance with an example.

Reference will now be made to the exemplary embodiments illustrated, andspecific language will be used herein to describe the same. It willnevertheless be understood that no limitation of the scope of theinvention is thereby intended.

DETAILED DESCRIPTION

Before the present invention is disclosed and described, it is to beunderstood that this invention is not limited to the particularstructures, process steps, or materials disclosed herein, but isextended to equivalents thereof as would be recognized by thoseordinarily skilled in the relevant arts. It should also be understoodthat terminology employed herein is used for the purpose of describingparticular examples only and is not intended to be limiting. The samereference numerals in different drawings represent the same element.Numbers provided in flow charts and processes are provided for clarityin illustrating steps and operations and do not necessarily indicate aparticular order or sequence.

Example Embodiments

An initial overview of technology embodiments is provided below and thenspecific technology embodiments are described in further detail later.This initial summary is intended to aid readers in understanding thetechnology more quickly and is not intended to identify key features oressential features of the technology, nor is it intended to limit thescope of the claimed subject matter.

A technology is described for collecting magnetic field gradientmeasurements, and then using the magnetic field gradient measurements asa navigation aid. A moving platform (e.g., a missile or an aircraft) cancontinuously take magnetic field gradient measurements while travelingto a destination. The magnetic field gradient measurements can be thatof the Earth's magnetic anomaly field. In one example, a magnetometeronboard the moving platform can measure the Earth's magnetic fieldgradients as the moving platform travels to the destination. Themagnetometer can be a coil vector magnetometer. The magnetometer canmeasure a change in the Earth's magnetic anomaly field as a function oftime. As a non-limiting example, the magnetometer can take magneticfield gradient measurements according to a range of approximately 2000to 50,000 times per second. The magnetic field gradient measurements canalso be referred to as a magnetic field gradient tensor. The magneticfield gradient tensor is a 3×3 matrix, so the magnetic field gradienttensor has nine components. While the platform is moving, themagnetometer may not measure all nine components at the same time.Rather, the magnetometer can measure the components associated with acurrent direction of the moving platform. Therefore, the magnetometercan measure a projection of the magnetic field gradient tensor onto thedirection of motion. In one example, the moving platform can travel tothe destination at a defined velocity, such as Mach 0.8 or 280meters/second.

In one configuration, the magnetometer can be coupled to a gyroscope.The gyroscope coupled to the magnetometer can be separate from agyroscope that is part of the Inertial Navigation System of the movingplatform. The gyroscope coupled to the magnetometer can compensate forerror in the magnetic field gradient measurements due to, for example,the relatively high velocity at which the moving platform is traveling.The relatively high velocity of the moving platform can cause highfrequency vibrations on the moving platform, which can create undesiredvoltage in the magnetometer coils, thereby resulting in less accuratemagnetic field gradient measurements. Thus, the gyroscope coupled to themagnetometer can compensate for fast vibration of the airframe.

In one example, the gyroscope coupled to the magnetometer can track adifference in orientation between the onboard inertial navigation systemand the magnetometer. In other words, the gyroscope coupled to themagnetometer can track a misalignment between an orientation of anairframe body coordinate system (in which the velocity of the movingplatform is measured) and an orientation of the magnetometer onboard themoving platform. The difference in orientation (or the misalignment) cancause error in the magnetic field gradient measurements. The gyroscopecoupled to the magnetometer can generate a correction value (e.g., arelative rotation matrix) to compensate for this error in the magneticfield gradient measurements. The correction value can be applied to themagnetic field gradient measurements with the errors, thereby resultingin magnetic field gradient measurements having a reduced level of error.Without the gyroscope onboard the fast moving platform to compensate forthe error due to the difference in orientation or misalignment, theaccuracy of the magnetic field gradient measurements would be below anacceptable level.

In another aspect of the current technology, the moving platform can usethe magnetic field gradient measurements for navigation purposes. Themagnetic field gradient measurements can be used as part of a magneticfield navigation system. In other words, the gradient of the Earth'sgeomagnetic anomaly field can be exploited to determine the movingplatform's position. The magnetic field navigation system can also bereferred to as magnetic aided INS navigation (MAIN). The moving platformcan utilize a global positioning system (GPS) aided inertial navigationsystem (INS). The magnetic field navigation system can be used in placeof GPS. In another example, the position provided by the magnetic fieldnavigation system can be used to correct for INS drift. Thus, anorientation of the gyroscope that is part of the moving platform's INSsystem (as opposed to the gyroscope that is coupled to the magnetometer)can be corrected for INS drift. The magnetometer onboard the movingplatform can continuously measure the magnetic field gradients of theEarth while the moving platform is traveling to the destination. In oneexample, the magnetic field gradients can be measured between 2,000times per second and 50,000 times per second. The sequence of magneticfield gradient measurements can correspond to the path traveled by themoving platform. The sequence of magnetic field gradient measurementscan be compared to a reference magnetic field gradient map. Inparticular, the sequence can be compared to a plurality of possibletrajectories derived from the reference magnetic field gradient map.Each of the possible trajectories is associated with a set of knownmagnetic field gradients. The reference magnetic field gradient map is atopographical map of the Earth's magnetic anomaly field. The referencemagnetic field gradient map can be provided by an external source, suchas the National Geophysical Data Center (NGDC). Based on the comparison,a trajectory derived from the reference magnetic field gradient map thatmost closely correlates to the sequence of magnetic field gradientmeasurements can be identified. In other words, the identifiedtrajectory can be inferred as being substantially the same trajectory(or path) taken by the moving platform. The trajectory can have knowngeographical coordinates, and therefore, the geographical location ofthe moving platform can be determined based on the known geographicalcoordinates of the trajectory. As a result, the moving platform candetermine its geographical location using the magnetic field navigationsystem and without reliance on GPS. In particular, the knowngeographical coordinates of the trajectory can be used to mitigateposition error of the moving platform. Thus, the known geographicalcoordinates can be used to improve an INS solution, and thereby, lead tothe determination of the moving platform's latitude, longitude andaltitude.

Measuring Magnetic Field Gradients

FIG. 1 illustrates an exemplary system for determining a magnetic fieldgradient of the Earth using a magnetometer 122 installed on a movingplatform 110 (e.g., an aircraft). The magnetic field gradient (ormagnetic field gradient tensor) can be of the Earth's magnetic anomalyfield. The magnetic field gradient can also refer to measured spatialvariations in the Earth's magnetic anomaly field. The magnetometer 122can be a vector magnetometer or an inductive coil vector magnetometer.The magnetometer 122 can be part of a measurement device 120 that isinstalled on the moving platform 110. The moving platform 110 can betraveling at a defined velocity (e.g., Mach 0.5 or higher). As explainedin greater detail below, magnetic field gradient measurements canprovide a navigation aid for the moving platform 110.

In one example, the magnetometer 122 can include a 3-axis coil magneticantenna to measure the magnetic gradient of the Earth's anomaly field.The magnetometer 122 can measure the magnetic field gradient while themoving platform 110 is traveling over land or water. The magneticantenna can take readings of the magnetic field as the moving platform110 (or airborne platform) moves along its trajectory. In oneconfiguration, the magnetometer 122 can continuously measure (e.g.,20,000 measurements per second) the magnetic field gradient associatedwith the moving platform's current position on the Earth.

In one configuration, with respect to performing the magnetic fieldgradient measurements, a magnetic coil of the magnetometer can generatevoltage that is proportional to a change of magnetic flux through thatmagnetic coil. The magnetic flux is described by: Flux through coil“i”=Ā_(i)·B; where i=x, y, z (1). The magnetometer can measure threecomponents: the changes of magnetic flux through each of the magneticcoils x, y and z. Each of these are described by: Voltage in coil

${{``i"} = {{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{d\overset{\rightharpoonup}{B}}{dt}}};$where i=x, y, z (2). Note that the subscript “i” can be used to describethe three components. If the magnetic coil is moved through a magneticfield, then the change in magnetic flux can be caused by threemechanisms. A first mechanism is the time dependent change of themagnetic field itself, whether the magnetic coil moves or does not move.A second mechanism is a change in orientation of the magnetic coil withthe magnetic field regardless of whether the magnetic field is constantor not constant. A third mechanism is the movement of the magnetic coilfrom a location with one value of the magnetic field to a location withanother value of the magnetic field.

The three components measured by the magnetometer are the termsdescribed by the three terms in the following equation:

$\begin{matrix}{{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial B}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial A_{i}}{\partial t}} + {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}} \cdot {\overset{\rightharpoonup}{v}.}}} & (3)\end{matrix}$The third term of the equation (i.e., Ā_(i)·∇B·

) can also be represented as

$\begin{matrix}{{{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}} \cdot \overset{\rightharpoonup}{v}} = {{\begin{matrix}A_{i}^{x} & A_{i}^{y} & A_{i}^{z}\end{matrix}} \cdot {\begin{matrix}\frac{\partial B_{x}}{\partial x} & \frac{\partial B_{x}}{\partial y} & \frac{\partial B_{x}}{\partial z} \\\frac{\partial B_{x}}{\partial y} & \frac{\partial B_{y}}{\partial y} & \frac{\partial B_{y}}{\partial z} \\\frac{\partial B_{x}}{\partial z} & \frac{\partial B_{z}}{\partial y} & \frac{\partial B_{z}}{\partial z}\end{matrix}} \cdot {{\begin{matrix}\frac{dx}{dt} \\\frac{dy}{dt} \\\frac{dz}{dt}\end{matrix}}.}}} & (4)\end{matrix}$

The first part of the third term of the equation (i.e., ∥A_(i) ^(x)A_(i) ^(y) A_(i) ^(z)∥) is a vector orientation of the coil “i”. Thesecond part of the third term of the equation

$\left( {{i.e.},{\begin{matrix}{{\partial B_{x}}/{\partial x}} & {{\partial B_{x}}/{\partial y}} & {{\partial B_{x}}/{\partial z}} \\{{\partial B_{x}}/{\partial y}} & {{\partial B_{y}}/{\partial y}} & {{\partial B_{y}}/{\partial z}} \\{{\partial B_{x}}/{\partial z}} & {{\partial B_{z}}/{\partial y}} & {{\partial B_{z}}/{\partial z}}\end{matrix}}} \right)$is a magnetic field gradient tensor. As shown, the magnetic fieldgradient tensor is a 3×3 matrix. The magnetic field is a vector withthree components, and the magnetic field gradient can exist when themoving platform travels in one of the three directions. The third partof the third term of the equation

$\left( {{i.e.},{\begin{matrix}{{dx}/{dt}} \\{{dy}/{dt}} \\{{dz}/{dt}}\end{matrix}}} \right)$is the platform velocity

. The velocity of the moving platform can be used as a tool in measuringthe magnetic field gradients.

In the present application, although the magnetic field gradient tensorhas nine components, the magnetometer onboard the moving platform maynot measure all nine components. Rather, the magnetometer can measurethe components associated with the direction of the moving platform.Thus, the three components of the product ∇

·

can be measured, which is the projection of the magnetic field gradientonto the direction of motion. In one example, the vertical component ofthis projection, or

_(s)·∇

·

, can be used.

The magnetometer can measure the magnetic field as the platform ismoving. As an example, the magnetometer can measure the magnetic fieldin Point A. The magnetometer can move to Point B and measure thecorresponding magnetic field. The magnetic field gradient in Point A canbe subtracted from the magnetic field gradient in Point B in order todetermine a change in the magnetic field gradient when the movingplatform travels from Point A to Point B. Therefore, the magnetometercan measure the change in magnetic field as a function of time.

In one configuration, as the flight trajectory is traversed, each coilof the magnetometer 122 can generate a voltage that is proportional tothe speed at which the platform 110 is traveling. The magnetometer 122can measure a signal that is proportional to a time derivative of themagnetic field sensed by the magnetometer 122. As the platform 110moves, the value of the time derivative is equal to the projection ofthe magnetic field gradient tensor upon the direction of a velocityvector (corresponding to the moving platform's velocity) multiplied byan amplitude of the velocity vector (or a ground velocity). Transientmagnetic phenomena can inject additional signal into the magnetic fieldgradient tensor outputted by the magnetometer 122.

In one configuration, the signal in the magnetometer 122 is determinedby the electromotive force in each of the three orthogonal coils thatcomprise the magnetometer 122 (e.g., a vector magnetometer). The signalfrom each of the coils is proportional to the change of the magneticflux through the coil as it moves through the magnetic field. The signalin each of the coils is:

${V_{i} = \frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt}},$wherein V_(i) is the voltage in the coil i,

_(i) is the orientation of coil i, and

is the magnetic field. In addition, the equation above can be expandedas follows:

${\frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt} = {{\frac{\partial\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{\partial t} + {{\nabla\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)} \cdot \frac{d\overset{\rightharpoonup}{r}}{dt}}} = {{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial\overset{\rightharpoonup}{B}}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}} + {\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}}} \right) \cdot \overset{\rightharpoonup}{v}}}}},$wherein ∇

is the magnetic gradient tensor, and

represents the platform velocity vector.

The magnetic field represented above includes a total magnetic fieldthat is exposed to by the magnetometer 122. The total magnetic fieldincludes the magnetic anomaly field of the Earth, as well as othersources that can generate a detectable magnetic field. The other sourcesinclude magnetic fields induced by globally occurring phenomenon such asspace weather, diurnal variations to the field, lightning strikes(nearby and far away), magnetic jammers set by adversaries, and powertransmission lines. Additionally, local magnetic sources such as fieldsgenerated by power supplies onboard the moving platform 110 and straymagnetic fields of the onboard motors and actuators can contribute tothe total magnetic field.

Each of these magnetic fields is grouped into one of the different termsof the equation above. For example, the term (

_(i)·∇

)·

describes the gradient of the magnetic field component in the directionof

_(i) differentiated over the direction of the velocity vector (

). This term represents the signal from the magnetometer 122. Thissignal is measured in the magnetic sensor coordinate system, assignified by the presence of vector

_(i). The term

_(i)·∂

/∂t describes the signal due to changes in the orientation of themagnetometer 122 in the external magnetic field. As described below,this is a noise source that is caused by mechanical vibration of themagnetometer 122. In one example, vibration caused by a motor iscorrelated with the variable magnetic field of that motor. The term

_(i)·∂

/∂t describes the signal due to temporal changes in a backgroundmagnetic field. These changes can be separated into two distinct groups:local environment and global environment. Local environment describesvariable magnetic fields generated by elements of the moving platform110 (e.g., an aircraft), such as motors, actuator, electronics, andferromagnetic elements of the moving platform 110. The globalenvironment refers to variable fields that are generated outside themoving platform 110, such as space weather and diurnal variation.

In one configuration, the magnetometer onboard the moving platform cancontinuously sample the magnetic field gradient. In other words, themagnetometer can perform high frequency sampling of the magnetic fieldgradient. The magnetometer can continuously output the magnetic fieldgradients as a function of time. As a non-limiting example, themagnetometer can measure the magnetic field gradient approximately 2,000times per second. As another non-limiting example, the magnetometer canmeasure the magnetic field gradient approximately 50,000 times persecond.

The moving platform 110 can travel at a defined velocity. As anon-limiting example, the defined velocity can be at least Mach 0.5. Themagnetometer 122 on the moving platform 110 can take measurements of themagnetic field gradient of the Earth as the moving platform 110 travelsat the defined velocity. In one example, the relatively high velocity ofthe moving platform 110 can cause a misalignment between a localcoordinate system associated with the moving platform 110 and anorientation of the magnetometer 122. In particular, the misalignment canbe a result of vibrations of the moving platform 110 due to therelatively high velocity of the moving platform 110. This misalignmentcan result in errors in the magnetic field gradient measurements. As anon-limiting example, when the moving platform 110 is traveling at aspeed of Mach 0.5 or higher, the amount of resulting error in themagnetic field gradient measurements due to the misalignment can bebeyond an acceptable noise level. As a result of the error, the magneticfield gradient measurements can be inaccurate. On the other hand, movingplatforms that travel at slower speeds have a reduced signal to noiseratio (SNR) as compared to moving platforms that travel at higherspeeds, which results in difficulty when isolating the real magneticfield from the error.

The high frequency vibrations can cause misalignment of the localcoordinate system associated with the moving platform 110 and anorientation of the magnetometer 122. The local coordinate system caninclude an airframe body coordinate system in which the velocity of themoving platform 110 is measured using global coordinates. In particular,an onboard navigation system that operates using the local coordinatesystem can provide the velocity (or velocity vector) for the movingplatform 110. The misalignment (or the difference in orientation betweenthe magnetometer and the onboard navigation system) can result inadditional noise in the magnetic field gradients measured at themagnetometer 122. As a result of the noise, the magnetic field gradientmeasurements can be inaccurate or invalid.

In one configuration, the magnetometer 122 can be coupled to a high rategyroscope 124. The magnetometer 122 coupled to the gyroscope 124 can bereferred to as a gradiometer. The gyroscope 124 can generate acorrection value that compensates for the error in the magnetic fieldgradient measurements due to the misalignment between the magnetometer122 and the onboard navigation system (e.g., the INS system). Since thegyroscope 124 coupled to the magnetometer 122 may not be coupled to theINS system, the high frequency vibrations of the mechanical frame of themoving platform can result in the errors in the magnetic field gradientmeasurements. The gyroscope 124 can also be referred to as acompensation gyroscope 124 that provides motion compensation. Inparticular, the gyroscope 124 can track a difference in orientationbetween the onboard navigation system (which operates using the localcoordinate system and provides the moving platform's velocity) and themagnetometer 122. The difference in orientation can be the correctionvalue. The correction value can also be referred to as a rotation matrixor a relative rotation matrix. The gyroscope 124 can operate in the highfrequency domain and provide the relative rotation matrix to relate amagnetometer antenna and the local coordinate system (e.g., the airframebody coordinate system). The rotation matrix can be 3×3 in size, whichcorresponds to the three dimensions X, Y and Z. The rotation matrix caneffectively fix the magnetometer's disorientation. The correction value(or rotation matrix), when applied to a magnetic field gradientmeasurement, having error can result in a magnetic field gradientmeasurement with a reduced level of error. Therefore, the gyroscope 124can effectively correct the orientation of the magnetometer 122. Thegyroscope 124 coupled to the magnetometer 122 for correcting theorientation can be distinct from a gyroscope that is part of the movingplatform's INS system.

As previously described, the magnetic field gradient can be calculatedbased on the magnetometer's orientation (as well as the voltage in thecoil, the magnetic field, and the velocity). Thus, if the orientation isinaccurate, the calculated magnetic field gradient can be inaccurate aswell. Therefore, the correction value (or rotation matrix) caneffectively correct or compensate for the inaccuracies in themagnetometer's orientation. As a result, the calculated magnetic fieldgradient can be substantially accurate, even when the magnetometer 122is disoriented due to the moving platform's high velocity.

In one configuration, a magnetic field gradient determination module 130can be onboard the moving platform 110. The magnetic field gradientdetermination module 130 can receive the signal (or 3-coil output) fromthe magnetometer 122. The signal can be low-pass-filtered, as well asrelated to the magnetic field gradient and the speed vector of themagnetometer 122 in an Earth-fixed coordinate system. The signal (oroutput) from the magnetometer 122 can be a projection of the magneticfield gradient onto the moving platform's velocity vector. In addition,the magnetic field gradient determination module 130 can receive thecorrection value from the gyroscope 124. The magnetic field gradientdetermination module 130 can reduce the error in the signal (i.e., themagnetic field gradient measurements) by applying the correction valueto the noisy magnetic field gradient measurements. In other words, themagnetic field gradient determination module 130 can calculate the threecomponents of the magnetic field gradient tensor in the local coordinatesystem as a product of the signal or 3-coil output provided by themagnetometer 122 and the 3×3 rotation matrix provided by the gyroscope124. Therefore, even when the magnetometer 122 becomes disoriented dueto the moving platform's relatively high speed and produces magneticfield gradient measurements with errors, the gyroscope 124 cancompensate for the error, such that accurate magnetic field gradientmeasurements are taken from the moving platform 110.

In one example, the gyroscope 124 operates alongside the magnetometer122 (or a magnetic antenna of the magnetometer 122) for the purpose ofcompensating for high frequency airframe vibrations (or platforminstability). The output of the magnetic antenna and the output of thegyroscope 124 (i.e., the rotation matrix) can be provided to asubsequent function to determine the components of the magnetic field(X, Y, and Z) in a local sensor coordinate system. The components can beconverted to a North East Down (NED) coordinate system of the movingplatform 110 (or airborne platform) in order to generate the magneticfield gradient components.

As shown in the equation

$\begin{matrix}{{{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial B}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial A_{i}}{\partial t}} + {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}} \cdot \overset{\rightharpoonup}{v}}},} & (3)\end{matrix}$the signal amplitude is proportional to the velocity (v). As thevelocity is increased, the amount of vibration can increase. Thecompensation gyroscope that is coupled to the magnetometer, as describedearlier, can mitigate this vibration. The velocity indirectlycontributes to the second term of the equation, or

$\overset{\rightharpoonup}{B} \cdot {\frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}.}$This term describes the magnetometer vibrating in the constant

field. The rotation of the magnetometer due to the vibration cannegatively impact the accuracy of the magnetic field gradientmeasurements. If the magnetometer vibrates without changing itsorientation, the term above is zero. If the magnetometer does notrotate, then the values of the individual components of

do not change. Therefore, the derivative of the second term is zero,which results in the whole second term being zero. Therefore, lineartranslation of the magnetometer does not cause extra noise in themagnetic field gradient measurements, whereas rotation of themagnetometer can cause additional noise in the magnetic field gradientmeasurements. Therefore, the gyroscope coupled to the magnetometer cancompensate for the magnetometer's rotation, which is measured by thegyroscope.

In one configuration, the magnetometer 122 is a vector magnetometer asopposed to a single coil magnetometer. While orientation variation ofthe single coil magnetometer cannot be compensated using a gyroscope, avector magnetometer output can be corrected for noise by using agyroscope.

In one configuration, the moving platform can include a magneticnavigation system (which includes the magnetometer coupled with a firstgyroscope) and an inertial navigation system that includes a secondgyroscope. In one example, the same gyroscope can be used for both themagnetic navigation system and the inertial navigation system. Over aperiod of time, the second gyroscope for the inertial navigation systemcan drift. As a non-limiting example, the inertial navigation system candrift by X degrees per minute. In order to determine how much thegyroscope has drifted, the magnetic field gradient measurements canprovide an independent source for determining the moving platform'slocation. Therefore, the magnetic field gradient measurements can beused to correct for orientation drift of the inertial navigationsystem's gyroscope (i.e., the second gyroscope).

In one example, the magnetic field gradient measurements can be affectedby noise in the system. Once source of the noise can be due to thevibration of the magnetometer. There are several ways in which thevibration of the magnetometer can impact the magnetic field gradientmeasurements that are being collected. In one example, the magnetometercan point in an incorrect direction as compared to the direction inwhich the inertial navigation system is pointing. For example, theinertial navigation system can be located in the nose of an aircraft,whereas the magnetometer can be located in the tail of the aircraft. Thefact that these two systems are not collocated can introduce certainerrors due to the vibration of the mechanical frame of the aircraft. Inone example, the vibration of the aircraft can create an undesiredsignal in the magnetometer, which is another source of noise in themagnetic field gradient measurements.

A compensation gyroscope (or the first gyroscope coupled to themagnetometer) can compensate for errors in the magnetic field gradientmeasurements due to the vibrations. The first gyroscope coupled to orcollocated with the magnetometer does not measure the slow rotation ofthe airframe, but rather can compensate for fast vibration of theairframe. This high frequency vibration can create an undesired voltage(or undesired signal) in the magnetometer coils, which causes errors inthe magnetic field gradient measurements. The correction value from thefirst gyroscope can compensate for errors due to vibrations that causethe magnetometer to vibrate, as well as the vibrations that cause themagnetometer to not be oriented correctly with the INS system.Therefore, the moving platform can include two separate gyroscopes—thefirst gyroscope is collocated with the magnetometer and the secondgyroscope is part of the INS system. The first gyroscope can compensatefor vibration of the magnetometer and undesired signals that are createdat the magnetometer due to the vibration. The second gyroscope that ispart of the INS system can be used for navigation of the movingplatform. Orientation drift of the second gyroscope can be correctedbased on a known orientation determined by the magnetic navigationsystem.

FIG. 2 illustrates an exemplary system and related operations fordetermining a magnetic field gradient of the Earth using a magnetometer222 installed on a moving vehicle 210. Non-limiting examples of themoving vehicle 210 can include an aircraft or a self-propelled guidedweapon, such as a missile. The magnetometer 222 (e.g., an induction coilvector magnetometer) can take magnetic field gradient measurements asthe moving vehicle 210 travels to a destination. The magnetometer 222can be part of a measurement device 220, such as a gradiometer. Themeasurement device 220 can also include a gyroscope 224. The gyroscope224 can compensate for measurement errors of the magnetometer 222. Themeasurement errors can result from noise in the magnetic field gradientmeasurements due to the moving vehicle's velocity. For example, if themoving vehicle's velocity exceeds a certain threshold (e.g., Mach 0.5),then the amount of noise in the magnetic field gradient measurements canexceed a noise threshold and the gyroscope 224 can be activated. Inother words, the gyroscope 224 can be used to reduce the noise in themagnetic field gradient measurements.

In one configuration, the magnetometer 222 can produce a noisy magneticfield gradient 226. As previously described, the noisy magnetic fieldgradient can result from a difference in orientation between themagnetometer 222 and an onboard navigation system (e.g., an INS system).The difference in orientation can occur due to the moving vehicle'srelatively high velocity, which causes vibrations in the mechanicalframe of the moving vehicle 210. The noisy magnetic field gradient 226can be provided to a magnetic field gradient determination module 230.In addition, the magnetic field gradient determination module 230 canreceive a rotation matrix 228 from the gyroscope 224. The rotationmatrix 228 can also be referred to as a correction value. The rotationmatrix 228 can be used to effectively reorient the magnetometer 222. Themagnetic field gradient determination module 230 can multiply the noisymagnetic field gradient 226 with the rotation matrix 228 in order toproduce a corrected magnetic field gradient 232. The corrected magneticfield gradient 232 can be a magnetic field gradient with a reducedamount of noise. As a result, even when the moving vehicle 210 travelsat a relatively high speed that would ordinarily result in noisymagnetic field gradients, the use of the gyroscope 224 can result inrelatively accurate magnetic field gradients. The relatively high speedcan cause vibration noise that can limit the usefulness of the signals,but the gyroscope 224 can effectively remove that vibration noise.

Using Magnetic Field Gradients as a Navigation Aid

GPS signals are vulnerable to jamming and spoofing, especially inAnti-Access, Area Denial (A2AD) regions. As the concern of GPS-denialbecomes more prevalent, the military's ability to maintain missionreadiness and carry out operations becomes jeopardized. This drives theneed for innovative capabilities to provide accurate navigation overextended periods of time and long distances, while acting independent ofthe GPS satellite network. The magnetic navigation system describedherein, referred to as Magnetic Aided INS Navigation (MAIN), provides atechnique for airborne platforms to navigate over long distances with nodependency on GPS.

The magnetic navigation system can utilize the measured magnetic fieldgradients (as described above) in order to provide a navigation aid. Themagnetic navigation system can exploit the gradient of the Earth'smagnetic anomaly field to provide error correction to onboard INS. Themagnetic navigation system can be capable of operating in all weatherconditions, day or night, over featureless terrain, over rough terrain,and over water. In addition, the magnetic navigation system can beeffective during long-range and high-speed missions. The magneticnavigation system can operate without using additional infrastructure(e.g., radio towers or satellites).

Another benefit of the magnetic navigation system is its robustness withrespect to jamming. Since magnetic waves are attenuated inverselyproportional to a distance cubed, a large amount of energy is needed todistort the magnetic field over even a relatively small area. For anadversary to jam the magnetic navigation system, a magnetic field wouldhave to be created that is strong enough to reach the system at theoperational altitude and have an effect on the magnetic field gradientthat is sensed by the system. For a mission of several hundredkilometers, the jamming signal would need to cover a large area to havean effect on the measured gradient value. Thus, the magnetic navigationsystem is substantially unsusceptible to jamming from adverse parties.

In one configuration, a moving platform (e.g., a cruise missile) canoperate effectively in an A2AD environment where GPS is jammed using thepresent technology. During a launch phase of the mission, the cruisemissile can be boosted in the direction of the target and guided usingan inertial navigation system (INIS). In this case, GPS is available tothe missile during launch and early in the cruise phase of the mission.At some point during the cruise phase, the missile enters the A2AD areaand no longer has access to the GPS satellite constellation. At thispoint, the missile can rely solely on the magnetic navigation system toguide the missile during the remainder of the cruise phase. The magneticnavigation system can guide the missile to a target area, at which timea terminal phase is initiated. During the terminal phase, the missilecan use more accurate seeker technology in order to guide the missile tothe target.

FIG. 3 illustrates a magnetometer 332 on a moving platform 310 thatmeasures a magnetic field gradient of the Earth. In particular, themagnetic field gradient is of the Earth's magnetic anomaly field. Insome examples, the magnetometer 332 is an induction coil vectormagnetometer, and the moving platform 310 is a missile. However, themoving platform 310 can also include aircrafts (e.g., airplanes,helicopters) or other weapon systems. The magnetometer 332 can beincluded in a magnetic field navigation system 330 that is installed onthe moving platform 310. The magnetic field navigation system 330 can beoperable to provide the moving platform 310 with navigationalcapabilities using a plurality of magnetic field gradient measurements.In one configuration, the magnetic field navigation system 330 can beactivated when a global positioning system (GPS) 320 on the movingplatform 310 is jammed or inoperable. In an alternative configuration,the magnetic field navigation system 330 can be utilized even when theGPS 320 is functioning correctly or is not jammed.

The moving platform 310 can also include a navigation subsystem (notshown in FIG. 3). The navigation subsystem can include an inertialmeasurement unit (IMU), an inertial navigation unit (INU) and a Kalmanfilter. The IMU provides accumulated velocity change and angle changethat corresponds to the trajectory of the moving platform 310 (e.g., anaircraft or weapon). These measurements are inputted to the INU forcomputation of a strapdown inertial navigation solution. Measurementsfrom the INU are integrated to form position, velocity and attitudeestimates for the moving platform 310. Errors in the IMU output anderrors in the inertial navigation solution can be corrected using theKalman filter. In other words, corrections to the INU can be providedvia the Kalman filter. In addition, the IMU can be calibrated using theGPS 320 before the moving platform 310 enters a GPS-denied area. Asexplained in greater detail below, the magnetic field navigation system330 can be used to correct drift in the INS.

In one example, the magnetometer 332 (e.g., via a magnetic antenna) cantake magnetic field gradient measurements as the moving platform 310travels to a destination. In the example shown in FIG. 3, the movingplatform 310 can take magnetic field gradient measurements whentraveling between positions A-H along a path to the destination. Inother words, the magnetometer 332 can take magnetic field gradientmeasurement at position A, position B, and so on. In one example, themagnetometer 332 can continuously take magnetic field gradientmeasurements (e.g., the magnetometer 332 can continuously takemeasurements of the magnetic field gradient at 2,000 measurements persecond or greater), and the moving platform's position estimate can bederived every so often (e.g., every 150 seconds or 56 km of travel). Forexample, the magnetometer 332 can take magnetic field gradientmeasurements at a rate of 2,000 measurements per second (or greater)over a duration of 150 seconds, and the magnetic field navigation system330 can provide the navigation aid based on this information.

As previously described, each coil of the magnetometer 332 can generatea voltage that is proportional to the speed at which the platform 310 istraveling. The magnetometer 332 can measure a signal that isproportional to a time derivative of the magnetic field sensed by themagnetometer 332. The signal in the magnetometer 332 is determined bythe electromotive force in each of the three orthogonal coils thatcomprise the magnetometer 332 (e.g., a vector magnetometer). The signalfrom each of the coils is proportional to the change of the magneticflux through the coil as it moves through the magnetic field. The signalin each of the coils is:

${V_{i} = \frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt}},$wherein V_(i) is the voltage in the coil i,

_(i) is the orientation of coil i, and

is the magnetic field. In addition, the equation above can be expandedas follows:

${\frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt} = {{\frac{\partial\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{\partial t} + {{\nabla\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)} \cdot \frac{d\overset{\rightharpoonup}{r}}{dt}}} = {{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial\overset{\rightharpoonup}{B}}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}} + {\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}}} \right) \cdot \overset{\rightharpoonup}{v}}}}},$wherein ∇

is the magnetic gradient tensor, and

represents the platform velocity vector.

The magnetometer 332 can provide measured values of a magnetic fieldtensor gradient. In an ideal scenario, the only magnetic field thatwould be present is the magnetic field of the Earth's magnetic anomalyfield, as it is the magnetic anomaly field that is used by the magneticfield navigation system 330. However, other sources (e.g., global andlocal sources) that will be measured by each individual magnetometercoil. In addition, there are other sources associated with the coilassembly and calibration. The coils of the magnetometer 332 can alsopick up changes of the magnetic flux due to the platform's motionthrough the Earth's magnetic field. The combined total magnetic fieldthat these sources make up is detected by the individual coil assembliesof the magnetometer 332. In one example, proper calibration of the coilassemblies can allow for changes in the magnetic field in a magneticsensor coordinate system to be accurately measured. In addition,knowledge of magnetometer orientation can allow for the change inmagnetic field in a global North East Down (NED) coordinate system to beextracted. By combining the change of magnetic field, magnetometer (orsensor) orientation, and the moving platform's speed, the value of themagnetic field gradient can be determined.

In the technology described herein, the sensed magnetic gradients anderrors that are internal to the moving platform 310 (e.g., due tomotors, actuators, electronics) are evaluated in a local sensorcoordinate system (or a magnetometer coordinate system). Themagnetometer 332 can be aligned with the aircraft body or weapon bodyand co-located (or not co-located) with the navigation subsystem. In theNED coordinate system, North, East, Down (NED) is a local level frame.North is defined as the X_(NE)-axis and East as the Y_(NE)-axis. Thus,by the right hand rule, the Z_(NE)-axis is the negative geodetic normal,or down. The origin moves with the missile or aircraft. The airframebody coordinate system has its origin at the center of gravity (CG) ofthe airframe. The airframe can be that of the moving platform 310. TheX-axis points out the nose, Y-axis points out the right wing when in theairframe-up configuration, and Z-axis points down.

FIG. 4 illustrates matching a sequence of magnetic field gradientmeasurements in a magnetic profile 420 to a reference magnetic fieldgradient map 430. The sequence in the magnetic profile 420 can becompared to the reference magnetic field gradient map 430 in order for amoving platform 410 to determine its geographical location. The sequenceof magnetic field gradients can be from a plurality of magnetic fieldgradient measurements taken using a magnetometer onboard the movingplatform 410 (as previously described in FIG. 3). In other words, theplurality of magnetic field gradient measurements can be compiled toform the magnetic profile 420. Each magnetic field gradient measurementincluded in the magnetic profile 420 is associated with a distinctposition on the Earth. In addition, each magnetic field gradientmeasurement is associated with the Earth's magnetic anomaly field. Sincethe gradient of the Earth's geomagnetic field is of interest, themagnetic profile 420 can include a series of measured spatial variationsin the Earth's magnetic field. A rate of change of the magnetic field(i.e., the gradient) can be measured using the magnetometer that isonboard the moving platform 410. The magnetic field gradientmeasurements can be along the moving platform's direction of motion.Thus, the magnetic profile 420 can include a history of magneticgradient measurements (or magnetic gradient tensor measurements) for themoving platform 410.

In the example shown in FIG. 4, the magnetic profile 420 can includemagnetic field gradient measurements for position A, position B,position C, position D and position E. Therefore, the magnetic profile420 can include a first value that corresponds to the magnetic fieldgradient measurement at position A, a second value that corresponds tothe magnetic field gradient measurement at position B, and so on. Thesequence of measurements included in the magnetic profile 420 cancorrespond to a path traveled by the moving platform 410. In otherwords, a portion of the moving platform's path can include travelingthrough positions A through E. In one example, the magnetic profile 420can indicate a rate of change in the magnetic field with respect to eachof the magnetic field gradient measurements.

In one configuration, the magnetic profile 420 can be compared to areference magnetic field gradient map 430. In other words, the sequenceof magnetic field gradient measurements included in the magnetic profile420 can be compared with the reference magnetic field gradient map 430.The reference magnetic field gradient map 430 is similar to a terrainmap or topographical map, but indicates a magnetic field gradient for agiven position on the Earth. The reference magnetic field gradient map430 can provide information about the Earth's magnetic anomaly field.The reference magnetic field gradient map 430 can be considered as atruth source for magnetic field gradient information. In one example,the reference magnetic field gradient map 430 is provided by theNational Geophysical Data Center (NGDC). The reference magnetic fieldgradient map 430 can provide a spatially stable representation of thegradient of the Earth's magnetic anomaly field. In one example, thereference magnetic field gradient map 430 can be periodically updated(e.g., every year or every five years).

In one example, the sequence of measurements in the magnetic profile 420can be compared with the reference magnetic field gradient map 430 inorder to identify a set of corresponding measurements from the referencemagnetic field gradient map 430. In other words, if the moving platform410 does not exactly know its geographical location (e.g., the movingplatform 410 has a general idea of its location, but with some level ofuncertainty), but has a set of previous magnetic field gradientmeasurements, those previous magnetic field gradient measurements can beattempted to be found in the reference magnetic field gradient map 430.By identifying those previous magnetic field gradient measurements onthe reference magnetic field gradient map 430, which are each associatedwith a known geographical location, the moving platform 410 candetermine its own geographical location. Thus, the sequence is a uniqueset of values, and these same values (in the same order) are searchedfor in the reference magnetic field gradient map 430. As previouslyexplained, the reference magnetic field gradient map 430 can be regardedas a truth source, so each gradient value on the map is associated witha known geographical location (e.g., longitude and latitude).

In one configuration, the sequence of measurements in the magneticprofile 420 can be compared to a plurality of possible trajectoriesderived from the reference magnetic field gradient map 430. Thesepossible trajectories can be generated based on a general knowledge ofthe moving platform's location (e.g., a general region in which themoving platform 410 is likely to be within). In addition, the possibletrajectories can be generated based on predicted trajectories of the INSonboard the moving platform 410. In other words, the INS can provide ageneral indication of the moving platform's movements, and based on thatinformation, the moving platform's most likely trajectories can bepredicted. In one example, the most likely trajectories can benegatively affected by navigation errors of the INS (e.g., gyroscope andaccelerometer drifts). However, if the moving platform's estimatedposition is determined, this estimated position can be used to improvethe accuracy of the INS.

Each possible trajectory can include a series of known magnetic fieldgradient values. A trajectory that most closely correlates to thesequence of magnetic field gradient measurements in the magnetic profile420 can be identified. In other words, the trajectory that is identifiedcan be inferred as being substantially the same trajectory that themoving platform 410 is following. The geographical coordinates of theidentified trajectory are known based on the reference magnetic fieldgradient map 430. As a result, the moving platform 410 can determine itsown geographical location based on the known geographical coordinates ofthe identified trajectory.

In one example, the accuracy of the estimated geographical location (orposition) of the moving platform 410 based on the magnetic fieldnavigation system can be subject to a number of error sources. Theseerror sources include intrinsic magnetic sensor errors, errors in themagnetic gradient maps, external magnetic sources (e.g., micropulsationsdiurnal variation, magnetic storms), environmental electromechanicalnoise aboard the vehicle, unpredictability of the INS errors, etc.

In one configuration, the moving platform 410 can update its INS withthe geographical location that is determined using the magneticnavigation system. INS drift can occur over time, which can affect theaccuracy of the INS. Therefore, the INS can periodically be informed ofan updated geographical location of the moving platform 410. As aresult, the impact of INS drift can be minimalized. In one example, themoving platform 410 can employ a Kalman filter to process measurementsfrom independent aiding sources to compensate for the inertialnavigation errors resulting from IMU imperfections, mechanicalmisalignments, and dynamic responses.

In one example, the moving platform 410 can be equipped with a magneticgradiometer (or magnetometer) and pre-existing magnetic gradient maps.The magnetic gradients can be sensed along the moving platform'strajectory, which can result in the magnetic profile 420 of the magneticgradients. When a sufficient number of sensed gradient values areavailable in the magnetic profile 420, a map matching algorithm can beused to fit the magnetic profile 420 to the stored magnetic gradient mapin order to determine the moving platform's location. In one example,measured magnetic field gradients (i.e., derived from the magneticantenna of the magnetometer and provided in a global coordinate system)can be compared with predicted magnetic field gradients (i.e., a set ofmagnetic gradient profiles based on values from a database or map ofmagnetic field gradients that are generated along predicted trajectoriesof the INS). In another example, a Non-Gaussian stochastic estimationtechnique can be used to estimate the moving platform's position fromthe magnetic field gradient measurements and the associated referencemap.

In one configuration, the number of magnetic field gradient measurementsincluded in the magnetic profile 420 can impact the accuracy of themagnetic field navigation solution. In general, a greater number ofmagnetic field gradient measurements can provide a more accuratemagnetic field navigation solution. For example, if the magnetic profile420 includes a series of fifty magnetic field gradient measurements,then the likelihood of the series being matched to a possible trajectory(that accurately reflects the actual trajectory of moving platform 410)is greater than if the magnetic profile 420 were to include a series ofonly ten magnetic field gradient measurements. The navigational accuracycan be dependent on the number and shape of the anomalies that aretraversed during the mission. In one example, the accuracy can improveafter three or more magnetic anomalies are traversed by the movingplatform 410. In another example, the moving platform 410 can obtain anincreased number of magnetic field gradient measurements in a reducedperiod of time when traveling at a relatively high speed. In otherwords, a slower speed implies that few magnetic anomalies are traversed,which leads to a less diverse path. As a result, a longer time period islikely in order to converge to a navigation solution.

In the example shown in FIG. 4, the magnetic profile 420 that includesthe sequence can be compared with the reference magnetic field gradientmap 430. As shown in FIG. 4, the reference magnetic field gradient map430 can illustrate magnetic field gradient values at particularpositions on the Earth. In particular, the magnetic profile 420 can becompared with a plurality of possible trajectories from the referencemagnetic field gradient map 430. The possible trajectories can include afirst possible trajectory 440, a second possible trajectory 450 and athird possible trajectory 460. The possible trajectories can be derivedfrom the reference magnetic field gradient map 430. Each possibletrajectory can comprise a series of individual magnetic field gradientmeasurements. In one example, the possible trajectories that areselected can be selected from a defined region 470 within the referencemagnetic field gradient map 430. The defined region 470 can bedetermined based on general knowledge of the moving platform's location.For example, the moving platform's starting location can be known, andbased on a period of time since the moving platform 410 startedtraveling from the starting location and a predicted average speed, thedefined region 470 can be determined. In other words, the defined region470 represents a likely region in which the moving platform 410 islocated at a particular time. As a result, the magnetic profile 420 doesnot need to be compared with a magnetic map of the entire Earth, butrather can be compared with a portion of the reference magnetic fieldgradient map 430.

In one example, the sequence of magnetic field gradient measurements inthe magnetic profile 420 can be compared with the first possibletrajectory 440, the second possible trajectory 450 and the thirdpossible trajectory 460, respectively. Based on the comparison, one ofthe possible trajectories (e.g., the second possible trajectory 450) canbe identified as being a closest match to the sequence of magnetic fieldgradient measurements in the magnetic profile 420. In other words, theknown magnetic field gradient values that comprise the second possibletrajectory 450 substantially match the magnetic field gradientmeasurements in the magnetic profile 410. Thus, in this example, thesecond possible trajectory 450 can be inferred as being substantiallythe same trajectory that is being followed by the moving platform 410.Since the geographical coordinates of the second possible trajectory 450are known, the moving platform's geographical location can bedetermined.

FIG. 5 illustrates an exemplary technique for measuring a magnetic fieldgradient. As previously discussed, individual coils of a magnetometercan measure the Earth's magnetic field. In addition, the individualcoils can pick up other magnetic field sources, such as space weather,temporal sources or man-made sources. In addition, there are sourcesassociated with the coil assembly and calibration. Proper calibration ofthe coil assemblies can allow for the change of magnetic field to beaccurately measured. By combining the change of magnetic field, sensororientation, and a platform speed, the magnetic field gradient can bedetermined.

In one example, a magnetic sensor motion compensation system can operateto correct errors in the magnetometer (e.g., orientation drift of themagnetometer). The motion compensation can operate separately from aninertial navigation system (INS) that is responsible for the platformorientation and velocity. The magnetometer (and magnetometer antenna) isnot likely to be co-located with the INS, so the magnetometer'sorientation is likely to be different. In addition, vibrationfrequencies that influence the magnetometer's signal can occur at ahigher rate than most general purpose INS are designed to handle.

FIG. 6 illustrates an exemplary output of a magnetometer along an actualflight trajectory of a moving platform. As shown in FIG. 6, the signal(e.g., a signal generated by a gradiometer), noise, bias, and discreteevents describe events that occur outside the moving platform. Theseevents occur in the global NED coordinate system and are modeled in thatcoordinate system. The signal NAV INS (e.g., an ideal INS output that isused to convert the signal into the magnetic sensor coordinate system inwhich the magnetometer is calibrated), the INS error and theelectro-mechanical noise and bias shown in FIG. 6 are related to thetransformation between the NED and the sensor coordinate system. Thecalibration, internal noise, discrete events and correlated noise shownin FIG. 6 take place aboard the moving platform and are modeled in theplatform body coordinate system.

FIG. 7 illustrates an exemplary technique for computing a magnetic fieldgradient in a sensor coordinate system. A rate of change of the magneticfield (i.e., the gradient) that a platform is measuring can bedetermined using the platform's location to query the magnetic gradientmaps. The queried gradient is in the NED coordinate system, and can betranslated to a magnetic sensor coordinate system. As shown in FIG. 7,the rate of change of the magnetic field with respect to time can becomputed in the sensor coordinate system.

In one configuration, a map matching algorithm can evaluate a set ofhypothetical candidate trajectories to determine a likelihood of any ofthese candidate trajectories being the correct trajectory of the movingplatform. In other words, the map matching algorithm determines thelikelihood of any one of the hypothetical trajectories being the onethat best represents the moving platform's actual trajectory. Thealgorithm selects the trajectory that is most likely to be correct, andbased on this trajectory, a measured position error can be computed.

The map matching algorithm can generate and evaluate a set ofhypothetical trajectories to determine which hypothetical trajectorymost closely represents the sensed trajectory. In this way, thealgorithm can obtain an estimate of the latitude, longitude, andaltitude correlated path that was flown. The hypothetical trajectoriesare generated based on the navigation solution, hypothetical initialposition, velocity errors and attitude errors.

Furthermore, the hypothetical magnetic measurement for each point on ahypothetical trajectory is determined using a magnetic sensor modelembedded in the algorithm which has access to a magnetic map database.The history of the hypothetical magnetic measurements is compared to thehistory of the sensor measurements for each of the hypotheticaltrajectories. This comparison yields a measure of the likelihood of aparticular hypothetical trajectory being the correct one relative to theother hypothetical trajectories. The algorithm can collect severalseconds worth (e.g., nominally 150 seconds) of sensor measurements. Aseach sensor measurement is received, the algorithm can update each ofthe hypothetical trajectories and update the likelihood calculation foreach trajectory. This is more computationally efficient when comparedwith the alternative of calculating the likelihood of each trajectorywhen the 150 seconds lapses.

The first step in calculating the hypothetical trajectories is todetermine the number of offsets that will be performed for eachmeasurement update in the measurement period (e.g., 150 seconds). Thisdetermination is performed prior to receiving any sensor measurementsfor the current measurement period and is based on the size of thesearch grid (σ_(RM)). In general, as the value of σ_(RM) decreases thecloser together the hypothetical trajectories will be. The algorithm canperform offsets for eight different types of data accounting forhypothetical initial attitude, position and velocity errors. The eighthypothetical trajectory offsets can be for a total number of differentattitude offset values about the north axis, a total number of differentattitude offset values about the east axis used, a number of differentposition offset values in the north direction, a number of differentposition offset values in the east direction, a number of differentposition offset values in the down direction, a number of differentvelocity offset values in the north direction, a number of differentvelocity offset values in the east direction, and a number of differentvelocity offset values in the down direction. The value of σ_(RM) caninitially be 60 meters. This value is increased as required to reducethe number of hypothetical trajectories due to memory and throughputconstraints. The offset size for attitude, position, altitude, andvelocity can be calculated. These offsets are used in the process forgenerating the hypothetical trajectories.

Each hypothetical trajectory can be updated each time a magnetic sensormeasurement is received. Upon receipt of a new magnetic sensormeasurement, the location, altitude and velocity for the current pointin each hypothetical trajectory is calculated. The hypotheticalvelocity, latitude, longitude, and altitude are the three values used asinputs to a sensor model. The sensor model returns the expectedmeasurement at the hypothetical location and with the hypotheticalvelocity. The value obtained from the sensor model will be comparedagainst the hypothetical rotations of the sensor measurement todetermine the likelihood of the each hypothetical trajectory being thesolution.

The sensor model has an embedded database of the rate of change (i.e.,gradient) of the magnitude of magnetic field in the down directionrelative to position in NED. The model then obtains

$\frac{\partial B_{z}}{\partial R_{N}},{\frac{\partial B_{z}}{\partial R_{E}}\mspace{14mu}{and}\mspace{14mu}\frac{\partial B_{z}}{\partial R_{D}}}$at the location and altitude for a hypothetical trajectory by usingtri-linear interpolation on the values obtained from the database. Therate of change of the magnitude of the magnetic field in the downdirection with respect to time is computed as follows:

${\frac{\partial B_{z - {hyp}}}{\partial t} = {\begin{bmatrix}\frac{\partial B_{z}}{\partial R_{N}} & \frac{\partial B_{z}}{\partial R_{E}} & \frac{\partial B_{z}}{\partial R_{D}}\end{bmatrix}{\overset{\rightarrow}{v}}_{e - {hyp}}^{NED}}},$which is the value used for comparison against

$\frac{\partial{\hat{B}}_{z}}{\partial t}$along all hypothetical trajectories to determine which trajectory is themost likely to be correct.

The map matching algorithm can compute and provide position errormeasurements to a navigation Kalman filter. The navigation Kalman filtercan process the measurements and provide strapdown equations withcorrections used to contain the error growth of the navigation solution.

FIG. 8 illustrates an exemplary system and related operations fordetermining a geographical location of a moving vehicle 810 based on aplurality of magnetic field gradient measurements 822 of the Earth. Themoving vehicle 810 can include, but is not limited to, a self-propelledweapon system (e.g., a missile) or an aircraft. The magnetometer 820(e.g., a vector magnetometer) can be installed onboard the movingvehicle 810. As the moving vehicle 810 travels along a path to adestination, the magnetometer 820 on the moving vehicle 810 can takemagnetic field gradient measurements 822. For example, the magnetometer820 can take a magnetic field gradient reading (corresponding to adistinct position on the Earth) X times per second for a duration of Yseconds. As a non-limiting example, the magnetometer 820 can collectmagnetic field gradient measurements at a rate of 2,000 measurements persecond (or greater) over a duration of 150 seconds. As a result, themagnetometer 820 can collect a plurality of magnetic field gradientmeasurements 822 that correspond to the moving vehicle's path. Theplurality of magnetic field gradient measurements 822 can be compiledinto a sequence and included in a magnetic profile 824. The magneticprofile 824 can represent the magnetic field gradients 822 that havebeen sensed by the magnetometer 820 while the moving vehicle 810 travelsto the destination.

The magnetic profile 824 can be provided to a location determinationmodule 840. In addition, potential trajectories 832 of the movingvehicle 810 can be determined by the location determination module 840.The potential trajectories 832 can be derived from a reference magneticfield gradient map 830 stored in a database. The location determinationmodule 840 can determine the potential trajectories 832 in real-time andat periodic intervals based on the reference magnetic field gradient map830. The potential trajectories 832 can be predicted based on the movingvehicle's last known position (e.g., as provided by GPS or INS systemsof the moving vehicle 810). The reference magnetic field gradient map isa topographical map representing the magnetic field at specificpositions of the Earth. In other words, the reference magnetic fieldgradient map provides known magnetic field values. Thus, the potentialtrajectories 832 can each comprise of a series of points (or magneticfield gradient values) that are selected from the reference magneticfield gradient map. These potential trajectories 832 are predicted asbeing traveled on by the moving vehicle 810. In other words, as themoving vehicle 810 travels along the path, the potential trajectories832 that the moving vehicle 810 might take are predicted.

The location determination module 840 can compare the magnetic profile824 with the potential trajectories 832 (or hypothetical trajectories)based on the database 830, and based on the comparison, the locationdetermination module 840 can identify the vehicle's trajectory 842. Inother words, the identified trajectory 842 includes magnetic fieldgradient values that most closely correlate to the magnetic fieldgradients 822 in the magnetic profile 824. Thus, this trajectory 842 canbe assumed as being the trajectory that is followed by the movingvehicle 810. In this example, a direct correlation is made betweenmeasured gradients and the map, but a set of gradient values on the mapare selected in order to perform the comparison. Since the geographicalcoordinates of the trajectory 842 are known, the moving vehicle'sgeographical location 844 can be determined. The geographical location844 can include a longitude and latitude that describes the movingvehicle's position. The geographical location 844 can be provided to aninertial navigation system (INS) 850 of the moving vehicle 810. Byreceiving an updated geographical location, the INS 850 can correct fordrift that occurs over time.

FIG. 9 depicts a flow chart of a method for determining a geographicallocation of a moving platform. The method can be executed asinstructions on a machine, where the instructions are included on atleast one computer readable medium or one non-transitory machinereadable storage medium. The method can be implemented using one or moreprocessors of the machine. The method can include the operation ofperforming magnetic field gradient measurements from the movingplatform, each magnetic field gradient corresponding to a position onthe Earth, the magnetic field gradients being continuously measuredwhile the moving platform is traveling along a path to a destination, asin block 910. The method can include the operation of creating asequence of magnetic field gradient measurements that correspond to thepath traveled by the moving platform, as in block 920. The method caninclude the operation of comparing the sequence of magnetic fieldgradient measurements for the path to a plurality of possibletrajectories derived from a reference magnetic field gradient map, as inblock 930. The method can include the operation of identifying atrajectory from the reference magnetic field gradient map thatcorrelates to the sequence of magnetic field gradient measurements, thetrajectory having known geographical coordinates, as in block 940. Themethod can include the operation of determining the geographicallocation of the moving platform based on the known geographicalcoordinates of the trajectory, as in block 950.

In one example, the method can further include the operation of updatingan inertial navigation system (INS) of the moving platform with thegeographical location in order to mitigate INS drift. In anotherexample, the operation of determining the geographical location includesdetermining latitude and a longitude associated with the moving platformbased on the trajectory identified from the reference magnetic fieldgradient map.

In one example, the method can further include the operation ofperforming the magnetic field gradient measurements using a magnetometerthat is onboard the moving platform. In another example, the movingplatform is traveling at a defined velocity of Mach 0.5 or greater. Inyet another example, the moving platform is a self-propelled guidedweapon or an aircraft. In addition, the magnetic field gradientmeasurements are of the Earth's magnetic anomaly field. In one example,determining the geographical location further comprises using the knowngeographical coordinates of the moving platform to mitigate positionserrors in a previous inertial navigation system (INS) solution.

In one example, the method can further include the operation ofperforming the magnetic field gradient measurements using a vectormagnetometer onboard the moving platform, wherein the vectormagnetometer includes a plurality of coils for performing the magneticfield gradient measurements, wherein a signal for each coil i isrepresented as

${V_{i} = \frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt}},$which is equal to

${{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial\overset{\rightharpoonup}{B}}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}} + {\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}}} \right) \cdot \overset{\rightharpoonup}{v}}},$wherein V_(i) is a voltage in the coil i,

_(i) is an orientation of the coil i,

is a magnetic field, ∇

is a magnetic gradient tensor, and

represents a moving platform velocity vector. In addition, each magneticfield gradient measurement is a projection of a magnetic field gradienttensor into a direction of motion associated with the moving platform.

FIG. 10 depicts a flow chart of a method for determining a geographicallocation. The method can be executed as instructions on a machine, wherethe instructions are included on at least one computer readable mediumor one non-transitory machine readable storage medium. The method can beimplemented using one or more processors of the machine. The method caninclude the operation of identifying a sequence of magnetic fieldgradient measurements for specific positions on the Earth thatcorrespond to a path traveled by a moving platform, as in block 1010.The method can include the operation of comparing the sequence ofmagnetic field gradient measurements for the path to a referencemagnetic field gradient map, as in block 1020. The method can includethe operation of identifying a trajectory from the reference magneticfield gradient map that correlates to the sequence of magnetic fieldgradient measurements, the trajectory having known geographicalcoordinates, as in block 1030. The method can include the operation ofdetermining the geographical location of the moving platform based onthe known geographical coordinates of the trajectory, as in block 1040.

In one example, the method can further include the operation of updatingan inertial navigation system (INS) of the moving platform with thegeographical location in order to mitigate INS drift. In anotherexample, the operation of determining the geographical location includesdetermining a latitude and a longitude associated with the movingplatform based on the trajectory identified from the reference magneticfield gradient map. In yet another example, the method can furtherinclude the operation of measuring each magnetic field gradientaccording to a defined frequency while the moving platform is travelingalong the path to a destination, wherein each magnetic field gradientcorresponds to a position on the Earth.

In one example, the method can further include the operation ofmeasuring each magnetic field gradient using an inductive coil vectormagnetometer that is onboard the moving platform. In another example,the operation of comparing further comprises comparing the sequence ofmagnetic field gradient measurements for the path to a plurality ofpossible trajectories derived from the reference magnetic field gradientmap. In yet another example, the reference magnetic field gradient mapis a topographical map of the Earth's magnetic anomaly field.

FIG. 11 illustrates a system 1100 for determining a geographicallocation of a moving platform 1120. The system 1100 can include a vectormagnetometer 1112 operable to measure a plurality of magnetic fieldgradients from the moving platform 1120. Each magnetic field gradientcan correspond to a position on the Earth. The magnetic field gradientscan be continually measured while the moving platform 1120 is travelingalong a path to a destination. The system 1100 can include a data storecomprising a reference magnetic field gradient map 1114 that describesthe Earth's magnetic anomaly field. The system 1100 can include one ormore processors 1116 operable to: identify the plurality of magneticfield gradients; create a sequence of magnetic field gradientmeasurements from the plurality of magnetic field gradients thatcorrespond to the path traveled by the moving platform 1120; compare thesequence of magnetic field gradient measurements for the path to aplurality of possible trajectories derived from the reference magneticfield gradient map 1114; identify a trajectory from the referencemagnetic field gradient map 1114 that correlates to the sequence ofmagnetic field gradient measurements, the trajectory having knowngeographical coordinates; and determine the geographical location of themoving platform 1120 based on the known geographical coordinates of thetrajectory.

In one example, the one or more processors 1116 are further configuredto update an inertial navigation system (INS) of the moving platform1120 with the geographical location in order to mitigate INS drift. Inanother example, the system 1100 is installed onboard the movingplatform 1120. In yet another example, the system 1100 is installedonboard a self-propelled guided weapon or an aircraft. In addition, thevector magnetometer 1112 includes a plurality of coils for measuring themagnetic field gradient, wherein a signal for each coil i is representedas

${V_{i} = \frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt}},$which is equal to

${{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial\overset{\rightharpoonup}{B}}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}} + {\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}}} \right) \cdot \overset{\rightharpoonup}{v}}},$wherein V_(i) is a voltage in the coil i,

_(i) is an orientation of the coil i,

is a magnetic field, ∇

is a magnetic gradient tensor, and

represents a moving platform velocity vector.

FIG. 12 depicts a flow chart of a method for determining a geographicallocation of a moving platform. The method can be executed asinstructions on a machine, where the instructions are included on atleast one computer readable medium or one non-transitory machinereadable storage medium. The method can be implemented using one or moreprocessors of the machine. The method can include the operation ofperforming magnetic field gradient measurements from the movingplatform, each magnetic field gradient corresponding to a position onthe Earth, the magnetic field gradients being continuously measuredwhile the moving platform is traveling along a path to a destination, asin block 1210. The method can include the operation of creating asequence of magnetic field gradient measurements that correspond to thepath traveled by the moving platform, as in block 1220. The method caninclude the operation of comparing the sequence of magnetic fieldgradient measurements for the path to a plurality of possibletrajectories derived from a reference magnetic field gradient map, as inblock 1230. The method can include the operation of identifying atrajectory from the reference magnetic field gradient map thatcorrelates to the sequence of magnetic field gradient measurements, thetrajectory having known geographical coordinates, as in block 1240. Themethod can include the operation of determining the geographicallocation of the moving platform based on the known geographicalcoordinates of the trajectory, as in block 1250.

In one example, the method can further include the operation of updatingan inertial navigation system (INS) of the moving platform with thegeographical location in order to mitigate INS drift. In anotherexample, the operation of determining the geographical location includesdetermining latitude and a longitude associated with the moving platformbased on the trajectory identified from the reference magnetic fieldgradient map.

In one example, the method can further include the operation ofperforming the magnetic field gradient measurements using a magnetometerthat is onboard the moving platform. In another example, the movingplatform is traveling at a defined velocity of Mach 0.5 or greater. Inyet another example, the moving platform is a self-propelled guidedweapon or an aircraft. In addition, the magnetic field gradientmeasurements are of the Earth's magnetic anomaly field. In one example,determining the geographical location further comprises using the knowngeographical coordinates of the moving platform to mitigate positionserrors in a previous inertial navigation system (INS) solution.

In one example, the method can further include the operation ofperforming the magnetic field gradient measurements using a vectormagnetometer onboard the moving platform, wherein the vectormagnetometer includes a plurality of coils for performing the magneticfield gradient measurements, wherein a signal for each coil i isrepresented as

${V_{i} = \frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt}},$which is equal to

${{{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial\overset{\rightharpoonup}{B}}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}} + {\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}}} \right) \cdot \overset{\rightharpoonup}{v}}},$wherein V_(i) is a voltage in the coil i,

_(i) is an orientation of the coil i,

is a magnetic field, ∇

is a magnetic gradient tensor, and

represents a moving platform velocity vector. In addition, each magneticfield gradient measurement is a projection of a magnetic field gradienttensor into a direction of motion associated with the moving platform.

FIG. 13 depicts a flow chart of a method for determining a geographicallocation. The method can be executed as instructions on a machine, wherethe instructions are included on at least one computer readable mediumor one non-transitory machine readable storage medium. The method can beimplemented using one or more processors of the machine. The method caninclude the operation of identifying a sequence of magnetic fieldgradient measurements for specific positions on the Earth thatcorrespond to a path traveled by a moving platform, as in block 1310.The method can include the operation of comparing the sequence ofmagnetic field gradient measurements for the path to a referencemagnetic field gradient map, as in block 1320. The method can includethe operation of identifying a trajectory from the reference magneticfield gradient map that correlates to the sequence of magnetic fieldgradient measurements, the trajectory having known geographicalcoordinates, as in block 1330. The method can include the operation ofdetermining the geographical location of the moving platform based onthe known geographical coordinates of the trajectory, as in block 1340.

In one example, the method can further include the operation of updatingan inertial navigation system (INS) of the moving platform with thegeographical location in order to mitigate INS drift. In anotherexample, the operation of determining the geographical location includesdetermining a latitude and a longitude associated with the movingplatform based on the trajectory identified from the reference magneticfield gradient map. In yet another example, the method can furtherinclude the operation of measuring each magnetic field gradientaccording to a defined frequency while the moving platform is travelingalong the path to a destination, wherein each magnetic field gradientcorresponds to a position on the Earth.

In one example, the method can further include the operation ofmeasuring each magnetic field gradient using an inductive coil vectormagnetometer that is onboard the moving platform. In another example,the operation of comparing further comprises comparing the sequence ofmagnetic field gradient measurements for the path to a plurality ofpossible trajectories derived from the reference magnetic field gradientmap. In yet another example, the reference magnetic field gradient mapis a topographical map of the Earth's magnetic anomaly field.

FIG. 14 illustrates a system 1400 for determining a geographicallocation of a moving platform 1420. The system 1400 can include a vectormagnetometer 1412 operable to measure a plurality of magnetic fieldgradients from the moving platform 1420. Each magnetic field gradientcan correspond to a position on the Earth. The magnetic field gradientscan be continually measured while the moving platform 1420 is travelingalong a path to a destination. The system 1400 can include a data storecomprising a reference magnetic field gradient map 1414 that describesthe Earth's magnetic anomaly field. The system 1400 can include one ormore processors 1416 operable to: identify the plurality of magneticfield gradients; create a sequence of magnetic field gradientmeasurements from the plurality of magnetic field gradients thatcorrespond to the path traveled by the moving platform 1420; compare thesequence of magnetic field gradient measurements for the path to aplurality of possible trajectories derived from the reference magneticfield gradient map 1414; identify a trajectory from the referencemagnetic field gradient map 1414 that correlates to the sequence ofmagnetic field gradient measurements, the trajectory having knowngeographical coordinates; and determine the geographical location of themoving platform 1420 based on the known geographical coordinates of thetrajectory.

In one example, the one or more processors 1416 are further configuredto update an inertial navigation system (INS) of the moving platform1420 with the geographical location in order to mitigate INS drift. Inanother example, the system 1400 is installed onboard the movingplatform 1420. In yet another example, the system 1400 is installedonboard a self-propelled guided weapon or an aircraft. In addition, thevector magnetometer 1412 includes a plurality of coils for measuring themagnetic field gradient, wherein a signal for each coil i is representedas

${V_{i} = \frac{d\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot \overset{\rightharpoonup}{B}} \right)}{dt}},$which is equal to

${{\overset{\rightharpoonup}{A}}_{i} \cdot \frac{\partial\overset{\rightharpoonup}{B}}{\partial t}} + {\overset{\rightharpoonup}{B} \cdot \frac{\partial{\overset{\rightharpoonup}{A}}_{i}}{\partial t}} + {\left( {{\overset{\rightharpoonup}{A}}_{i} \cdot {\nabla\overset{\rightharpoonup}{B}}} \right) \cdot}$

, wherein V_(i) is a voltage in the coil i,

_(i) is an orientation of the coil i,

is a magnetic field, ∇

is a magnetic gradient tensor, and

represents a moving platform velocity vector.

Various techniques, or certain aspects or portions thereof, may take theform of program code (i.e., instructions) embodied in tangible media,such as floppy diskettes, CD-ROMs, hard drives, non-transitory computerreadable storage medium, or any other machine-readable storage mediumwherein, when the program code is loaded into and executed by a machine,such as a computer, the machine becomes an apparatus for practicing thevarious techniques. In the case of program code execution onprogrammable computers, the computing device may include a processor, astorage medium readable by the processor (including volatile andnon-volatile memory and/or storage elements), at least one input device,and at least one output device. The volatile and non-volatile memoryand/or storage elements may be a RAM, EPROM, flash drive, optical drive,magnetic hard drive, or other medium for storing electronic data. One ormore programs that may implement or utilize the various techniquesdescribed herein may use an application programming interface (API),reusable controls, and the like. Such programs may be implemented in ahigh level procedural or object oriented programming language tocommunicate with a computer system. However, the program(s) may beimplemented in assembly or machine language, if desired. In any case,the language may be a compiled or interpreted language, and combinedwith hardware implementations.

It should be understood that many of the functional units described inthis specification have been labeled as modules, in order to moreparticularly emphasize their implementation independence. For example, amodule may be implemented as a hardware circuit comprising custom VLSIcircuits or gate arrays, off-the-shelf semiconductors such as logicchips, transistors, or other discrete components. A module may also beimplemented in programmable hardware devices such as field programmablegate arrays, programmable array logic, programmable logic devices or thelike.

Modules may also be implemented in software for execution by varioustypes of processors. An identified module of executable code may, forinstance, comprise one or more physical or logical blocks of computerinstructions, which may, for instance, be organized as an object,procedure, or function. Nevertheless, the executables of an identifiedmodule need not be physically located together, but may comprisedisparate instructions stored in different locations which, when joinedlogically together, comprise the module and achieve the stated purposefor the module.

Indeed, a module of executable code may be a single instruction, or manyinstructions, and may even be distributed over several different codesegments, among different programs, and across several memory devices.Similarly, operational data may be identified and illustrated hereinwithin modules, and may be embodied in any suitable form and organizedwithin any suitable type of data structure. The operational data may becollected as a single data set, or may be distributed over differentlocations including over different storage devices, and may exist, atleast partially, merely as electronic signals on a system or network.The modules may be passive or active, including agents operable toperform desired functions.

Reference throughout this specification to “an example” or “exemplary”means that a particular feature, structure, or characteristic describedin connection with the example is included in at least one embodiment ofthe present invention. Thus, appearances of the phrases “in an example”or the word “exemplary” in various places throughout this specificationare not necessarily all referring to the same embodiment.

As used herein, a plurality of items, structural elements, compositionalelements, and/or materials may be presented in a common list forconvenience. However, these lists should be construed as though eachmember of the list is individually identified as a separate and uniquemember. Thus, no individual member of such list should be construed as ade facto equivalent of any other member of the same list solely based ontheir presentation in a common group without indications to thecontrary. In addition, various embodiments and example of the presentinvention may be referred to herein along with alternatives for thevarious components thereof. It is understood that such embodiments,examples, and alternatives are not to be construed as defactoequivalents of one another, but are to be considered as separate andautonomous representations of the present invention.

Furthermore, the described features, structures, or characteristics maybe combined in any suitable manner in one or more embodiments. In thefollowing description, numerous specific details are provided, such asexamples of layouts, distances, network examples, etc., to provide athorough understanding of embodiments of the invention. One skilled inthe relevant art will recognize, however, that the invention can bepracticed without one or more of the specific details, or with othermethods, components, layouts, etc. In other instances, well-knownstructures, materials, or operations are not shown or described indetail to avoid obscuring aspects of the invention.

While the forgoing examples are illustrative of the principles of thepresent invention in one or more particular applications, it will beapparent to those of ordinary skill in the art that numerousmodifications in form, usage and details of implementation can be madewithout the exercise of inventive faculty, and without departing fromthe principles and concepts of the invention. Accordingly, it is notintended that the invention be limited, except as by the claims setforth below.

What is claimed is:
 1. A system for performing magnetic field gradientmeasurements, the system comprising: an inductive coil vectormagnetometer that is onboard a moving platform, the inductive coilvector magnetometer operable to perform the magnetic field gradientmeasurements for specific positions on the Earth from the movingplatform; a gyroscope, coupled to the vector magnetometer, that isoperable to generate a correction value to compensate for error in themagnetic field gradient measurements captured by the inductive coilvector magnetometer; and one or more processors operable to: identifythat the magnetic field gradient measurements are affected by a level oferror that exceeds a defined threshold; identify the correction valuegenerated at the gyroscope to compensate for the error in the magneticfield gradient measurements; and apply the correction value generated atthe gyroscope to the magnetic field gradient measurements in order toobtain magnetic field gradient measurements with a reduced level oferror, wherein the correction value received from the gyroscopecomprises a relative rotation matrix and is applied to the magneticfield gradient measurements to relate a coil vector magnetometer antennaand an airframe body coordinate system to compensate for high frequencyairframe vibrations that causes disorientation of the inductive coilvector magnetometer.
 2. The system of claim 1, wherein the correctionvalue compensates for a misalignment between an orientation of theairframe body coordinate system associated with the moving platform andan orientation of the magnetometer onboard the moving platform.
 3. Thesystem of claim 1, wherein the error is caused by the high frequencyairframe vibrations on the moving platform due to a speed of the movingplatform.
 4. The system of claim 1, wherein the magnetic field gradientmeasurements are performed according to a range of approximately 2000 to50,000 times per second.
 5. The system of claim 1, wherein a magneticfield gradient measurement is a projection of a magnetic field gradienttensor into a direction of motion associated with the moving platform.6. The system of claim 1, wherein the moving platform is traveling at adefined velocity of Mach 0.5 or greater.
 7. The system of claim 1,wherein the moving platform is a self-propelled guided weapon or anaircraft.
 8. A system for determining a magnetic field gradient, thesystem comprising: a vector magnetometer onboard a moving platform; agyroscope onboard the moving platform and coupled to the vectormagnetometer; and one or more processors operable to: measure themagnetic field gradient for specific positions on the Earth using thevector magnetometer onboard the moving platform, the magnetic fieldgradient being affected by error that is caused by an orientationmisalignment of the vector magnetometer and a body coordinate system ofthe moving platform; generate a correction value to compensate for theerror in the magnetic field gradient using the gyroscope that is onboardthe moving platform; and apply the correction value to the magneticfield gradient in order to reduce the error in the magnetic fieldgradient caused by the orientation misalignment of the vectormagnetometer, wherein the correction value comprises a relative rotationmatrix and is applied to the magnetic field gradient to relate a coilvector magnetometer antenna and an airframe body coordinate system tocompensate for high frequency airframe vibrations that causesdisorientation of the inductive coil vector magnetometer.
 9. The systemof claim 8, wherein the one or more processors are further operable togenerate the correction value to compensate for the error in themagnetic field gradient when an error level exceeds a defined threshold.10. The system of claim 8, wherein the one or more processors arefurther operable to generate the correction value to compensate for theerror in the magnetic field gradient when the moving platform istraveling at a velocity that exceeds a defined threshold.
 11. The systemof claim 8, wherein the one or more processors are further operable togenerate the correction value to compensate for the error in themagnetic field gradient when the moving platform is traveling at adefined velocity of Mach 0.5 or greater.
 12. The system of claim 8,wherein the correction value is provided by the gyroscope onboard themoving platform.
 13. The system of claim 8, wherein the error is causedby the high frequency airframe vibrations on the moving platform due toa speed of the moving platform.
 14. The system of claim 8, wherein themagnetic field gradient is of the Earth's magnetic anomaly field. 15.The system of claim 8, wherein the one or more processors are furtheroperable to determine the magnetic field gradient by converting themagnetic field gradient from a local coordinate system to a North EastDown (NED) coordinate system of the moving platform.
 16. A system fordetermining a magnetic field gradient, the system comprising: a vectormagnetometer operable to measure the magnetic field gradient forspecific positions on the Earth; a gyroscope, coupled to the vectormagnetometer, that is operable to generate a correction value tocompensate for error in the magnetic field gradient; and one or moreprocessors operable to: identify the magnetic field gradient; identifythe correction value; and apply the correction value to the magneticfield gradient, wherein the vector magnetometer and the gyroscope areonboard a moving platform, wherein the correction value received fromthe gyroscope comprises a relative rotation matrix and is applied to themagnetic field gradient to relate a coil vector magnetometer antenna andan airframe body coordinate system to compensate for high frequencyairframe vibrations that causes disorientation of the inductive coilvector magnetometer.
 17. The system of claim 16, wherein the gyroscopeis operable to generate the correction value when the error in themagnetic field gradient exceeds a defined threshold and the movingplatform is traveling at a defined velocity.
 18. The system of claim 16,wherein the error in the magnetic field gradient is caused by amisalignment of a local coordinate system associated with the movingplatform and an orientation of the vector magnetometer.